双模态冲压发动机中的模态转换研究综述  

An Overview on Mode Transition in Dual Mode Ramjet

作　　者：张岩[1,2] 朱韶华[1] 刘刚[1] 李轩[1] 徐旭[1] 

机构地区：[1]北京航空航天大学宇航学院,北京100191 [2]南阳理工学院土木工程学院,河南南阳473004

出　　处：《推进技术》2013年第12期1719-1728,共10页Journal of Propulsion Technology

基　　金：双模态冲压发动机模态转换过程中的迟滞问题研究(51276007)

摘　　要：在以双模态冲压发动机为推进装置的高超声速飞行器的加速过程中,燃烧室内的释热量及其分布必须做出相应的调整,使得发动机从亚燃模态转换为超燃模态。在模态转换过程中,由于燃烧室下游边界条件突然从热力壅塞状态变为无壅塞状态,其壁面压力分布会发生明显改变。这将使作用在飞行器上的推力和动量发生突然变化,可能会导致飞行器失去控制。因此,如何实现不同燃烧模态的平稳转换,是燃烧室设计中的技术难点。本文详细介绍了双模态冲压发动机中不同燃烧模态的定义和判定准则、模态转换的实现方式、模态转换的机理,以及在模态转换时可能存在的激波反射结构转换迟滞和火焰结构转换迟滞现象。A ram-scram transition will occur at some time during the ascent of a hypersonic vehicle powered by a dual-mode ramjet. During this transition, the abrupt change of the downstream boundary con- dition from the thermally choked condition to the unchoked flow occurs. The ram-scram transition causes a change on the wall static distribution. This leads to a corresponding abrupt change in the thrust force and moments on the vehicle which may result in loss of vehicle control. Consequently, it is paramount important to achieve the smooth mode transition in the design of the combustor. In this paper, the classification of combustion modes, as well as the method and mechanism of mode transition, are introduced in detail. Furthermore, the possible hysteresis phenomena of shock wave reflection and flame structure during the mode transition are also discussed.

关 键 词：双模态冲压发动机 超燃模态 亚燃模态 模态转换 迟滞 

分 类 号：V235.21[航空宇航科学与技术—航空宇航推进理论与工程]